US3398640A - Rocket launcher device - Google Patents

Rocket launcher device Download PDF

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Publication number
US3398640A
US3398640A US601689A US60168966A US3398640A US 3398640 A US3398640 A US 3398640A US 601689 A US601689 A US 601689A US 60168966 A US60168966 A US 60168966A US 3398640 A US3398640 A US 3398640A
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US
United States
Prior art keywords
ignition
rocket
tube
sleeve
launching
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US601689A
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English (en)
Inventor
Apotheloz Robert
Schenk Hanspeter
Gelbert Alex
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
OC Oerlikon Corp AG Pfaeffikon
Original Assignee
Oerlikon Buehrle Holding AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Oerlikon Buehrle Holding AG filed Critical Oerlikon Buehrle Holding AG
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Publication of US3398640A publication Critical patent/US3398640A/en
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Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B4/00—Fireworks, i.e. pyrotechnic devices for amusement, display, illumination or signal purposes
    • F42B4/22—Fireworks, i.e. pyrotechnic devices for amusement, display, illumination or signal purposes characterised by having means to separate article or charge from casing without destroying the casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A19/00—Firing or trigger mechanisms; Cocking mechanisms
    • F41A19/06—Mechanical firing mechanisms, e.g. counterrecoil firing, recoil actuated firing mechanisms
    • F41A19/25—Mechanical firing mechanisms, e.g. counterrecoil firing, recoil actuated firing mechanisms having only slidably-mounted striker elements, i.e. percussion or firing pins
    • F41A19/27—Mechanical firing mechanisms, e.g. counterrecoil firing, recoil actuated firing mechanisms having only slidably-mounted striker elements, i.e. percussion or firing pins the percussion or firing pin being movable relative to the breech-block
    • F41A19/29—Mechanical firing mechanisms, e.g. counterrecoil firing, recoil actuated firing mechanisms having only slidably-mounted striker elements, i.e. percussion or firing pins the percussion or firing pin being movable relative to the breech-block propelled by a spring under tension
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/045—Rocket or torpedo launchers for rockets adapted to be carried and used by a person, e.g. bazookas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/077—Doors or covers for launching tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C7/00—Fuzes actuated by application of a predetermined mechanical force, e.g. tension, torsion, pressure
    • F42C7/12—Percussion fuzes of the double-action type, i.e. fuzes cocked and fired in a single movement, e.g. by pulling an incorporated percussion pin or hammer

Definitions

  • An ignition device for the starting of rockets wherein the rocket, having a propellant charge, is arranged as a connecting member between a launching trigger arranged on a projector before the same and an ignition casing located behind the same.
  • a common support spring supports the ignition casing via the rocket under a pressure eifective towards the front toward the launching trigger.
  • the launching trigger releases the support, so that the following relative movement of the ignition casing towards the projector begins with a triggering of a ball lock securing a detonator percussion pellet of the fuze, whereby the propellant charge is ignited.
  • the invention relates to an ignition device for the launching of rockets from a launcher tube, at the rear end of which there is fitted an ignition device for the rocket, a launching release and a locking component of the ignition device slidably guided in the direction of the launcher tube axis to release a striker, which under the pressure of a spring causes ignition by piercing a primer.
  • An object of the present invention is to provide an ignition device which is easily constructed and easy to manipulate, even if a rifleman has only one hand free for operating it.
  • a further object consists in avoiding connecting parts arranged at the exterior of the launching tube.
  • a still further object resides in having a minimum of mechanical nonelectrical parts as possible to accomplish several functions at the same time.
  • a further object of the invention is to provide the launching release in a zone on the launcher tube in which the firer can most safely and effectively hold the launcher device in his hands and actuate the launching release.
  • the aiming accuracy is thereby raised and the risk of injury eliminated.
  • any external connection between the launching release in front and the ignition device behind, which would be disturbing and weight-increasing, is unnecessary, and therefore the supporting of the launcher tube on the ground, for example, in no way affects the safety of operation of the launcher device.
  • FIGURE 1 is a longitudinal cross-sectional view with parts shown in elevation of a rocket launcher with the elements in position for launching.
  • FIGURE 2 is a cross-sectional view of the front of the launcher tube showing the cap in actuating position.
  • FIGURE 3 is a view similar to FIGURE 1 of a second embodiment of the launcher device.
  • FIGURE 4 is a cross-sectional view taken upon section line IV-IV looking in the direction of the arrows.
  • FIGURE 5 is a cross-sectional view through the igni- 3,398,640 Patented Aug. 27, 1968 "ice tion device of the form of the invention shown in FIG- URE 1 with the parts in safe position, and
  • FIGURE 6 is a view similar to that of FIGURE 5 with the parts in firing position.
  • a launcher tube 2 forms a main component of a transporting container 1, containing a light rocket 8 with a propellant charge, the combustion gases of which during the flight emit through outflow nozzle 58 towards the rear in the tail, in the base plate 3 of which an ignition device is arranged.
  • a locking component 9 is slidably supported in the ignition device.
  • the diameter of a head piece 20 of the sleeve 15, lying behind the end face of the base plate 3, is made smaller than the diameter of the bore 4 in the base plate 3.
  • a U- shaped arming spacer fork 21, half surrounding the sleeve 15, is arranged between this head piece 20 and the end face of the base plate 3.
  • the head piece 20 and the spacer fork 21 project into a recess 23 of a sealing cap 22 screwed on to the base plate 3.
  • the front face of the rocket 8 constructed as an abutment surface 28, rests against safety balls 30 under the influence of the force exerted by the spring 11 through the two discs 12 and 29, from which the latter one is provided with a continuous central bore 57, slidable in the launcher tube 2, on the rear end face 27 of the rocket.
  • the balls 30 are held in engagement with a rounded circular groove 32 on the inside of the wall of the launcher tube 2, by a cap 31 closing the transporting container 1 in front.
  • leaf springs 33 are gripped at equal angular spacings, which engage in the groove 32 and the launcher tube 2 between the individual safety balls 30, and serve to secure the cap 31. Together with the lanyard 34, secured to the cap 31 and the pull ring 56, a launching release is formed.
  • the mode of operation of the rocket launcher device is as follows.
  • the transporting container 1 now serving as a launcher tube, is supported with its totally enclosed rear end on the ground, for example, and held with one hand in the firing position by a firer, not shown.
  • the striker 16 is additionally prestressed, because the striker 16 is still coupled to the sleeve 15 and hence cannot take part in the movement of the locking component 9.
  • the balls 19 are pressed outwards into the annular cavity of the bore section 6 by a force transmitted by the surface of the recess 17 of the striker 16, so that the striker becomes free and is thrown by the spring 26 against the primer 10, which then ignites the charge 13.
  • the rocket 8 is driven out of the launcher tube 1, whereat, in a way not further explained here, the propellant charge 35 in the tail portion, serving for self-propulsion of the rocket 8, is ignited.
  • the striker 16 can only become freed if the sleeve 15 is held back by the arming spacer fork 21 on the forward movement of the locking component 9 of the ignition device. This fact is made use of during the assembly, i.e., when inserting the rocket 8 and the ignition device in the transporting container 1, Satisfactory sliding of the rocket 8 in the tube 2 under the pressure of the spring 11, on actuating the launching release, can thus be checked without the ignition being triggered provided the arming spacer fork 21 is not previously inserted.
  • the sleeve 15 and the striker 16 coupled to it can, in this case, move forward together with the locking component 9, without the locking component 9 being shifted in relation to the sleeve 15, because the diameter of the head piece 20 of the sleeve 15 is, of course, smaller than the diameter of the bore 4 of the base plate 3.
  • FIG. illustrates this position in the condition of fitting the ignition device.
  • the ignition device is then only armed when the arming spacer fork 21 is inserted (see FIG. 1).
  • FIG. 6 shows the condition of the ignition device in the firing position. It can there be seen that, as a result of actuating the launching release, the locking component 9 has moved in relation to the sleeve 15. Thereby the balls 19 were able to emerge radially over the guiding edge 55 and free the striker 16.
  • the locking component 9 of the ignition device is supported in the bore of a sleeve 36, which is rigidly connected with a launcher tube 38 by means of ribs 37.
  • the sleeve 36 accordingly here fulfills the same function as the base plate 3 of the first embodiment, namely guidance of the locking component 9 of the ignition device.
  • the locking component 9, under the pressure of the spring 11, is here supported directly on the tail portion of the rocket body 39 which contains a propellant charge 52 with corresponding outflow nozzle 58 which rocket body is guided in the launcher tube 38 by the shrouded fin unit 40, rigidly connected to it by the ribs 41 and furthermore by its head 42 containing an explosive charge.
  • a sleeve 43 is slid over the front end of the launcher tube 38, in which a groove 44 is cut, extending over the whole circumference of the inner wall.
  • a slit spring ring 45 arranged in the groove 44 engages in a groove 46 cut in the outside wall of the launcher tube 38. The ring 45 thereby secures the sleeve 43 against unwanted sliding on the launcher tube 38, but permits rotation of the sleeve 43 in relation to the tube 38.
  • a further groove 47 of trapezoidal cross section is only formed in a portion of the circumference of the inside wall of the sleeve 43 (FIG. 4).
  • a transverse hole 48 completely penetrating the sleeve wall, opens into one end of the groove 47.
  • a ball 49 the diameter of which is less than the diameter of the transverse hole 48 in the groove 47, engages in the other end of the groove 47 and furthermore into the interior of the tube 38, through a hole"50 completely penetrating the wall of the launcher tube 38.
  • a head 53 projecting forward from the rocket body 39, prevents the ball 49 from emerging from the groove 47 and the hole 50 in the launcher tube 38.
  • a ring-shaped supporting surface 51, of the rocket .39 forming a part of the surface of a cone of a large generating angle, is pressed against the ball 49, which thereby secures the rocket against sliding forward.
  • the sleeve 43 and the ball 49 therefore form the launching release.
  • an additional spring 54 can be inserted between the ribs 37 of the sleeve 36 and the ribs 41 of the shrouded fin unit of the rocket body 39.
  • the ignition device In order to release the ignition device, with the other hand, at the same time supporting the launcher tube 38, he rotates the sleeve 43, whereby the groove 47 shifts in relation to the ball 49 held in the wall of the tube 38, until the transverse hole 48 lies in the region of the ball 49.
  • the ball 49 is then pressed outwards by the supporting surface 51 with the forward movement of the rocket 39. Under the pressure of the spring 11, the locking component 9 of the ignition device now moves forward, pushing out the rocket 39 in front of it.
  • the striker 16 is set free, in the manner already described, to pierce the primer 10, so that ignition of the propellant charge 52 of the rocket 39 follows immediately after ignition of the primer 10, wherewith the discharge is released.
  • Ignition device for the launching of rockets comprising in combination a launcher tube, manually operated launching trigger for triggering the ignition, a bottom part fastened to said tube, a rocket axially displaceable in said tube having a propellant charge, an outflow nozzle communicating with said propellant charge directed towards the rear, a support shoulder on said rocket, an ignition casing in said bottom part located behind said rocket axially displaceable relative to said bottom part, and having a guiding edge on its rearward side, ignition elements in said casing controlled by said guiding edge for the ignition of said propellant charge through said outflow nozzle, a support spring pretensioned on one hand .on said bottom part of said tube and on the other hand on said ignition casing, whereby said ignition casing under the pressure of said support spring is urged towards the front of said rocket and said rocket with said support shoulder and said launching trigger is supported detachably so that when operating said launching trigger said support spring, said ignition casing and said rocket are pushed towards the front, whereby said guiding edge releases
  • Ignition device for the launching of rockets comprising in combination a launcher tube, a launching trigger at the front end .of said tube for triggering the ignition, said tube having an annular groove in the interior wall thereof, a locking member located in said annular groove, a manually removable trigger member with which said locking member interlocks, a bottom part located at the end of said tube opposite said trigger member, a rocket axially displaceable in said tube having a propellant charge, an outflow nozzle communicating with said charge directed towards the rear, a support shoulder on said rocket in engagement with said locking member, an ignition casing in said bottom part behind said rocket axially displaceable relative to said bottom part, having a guiding edge on its rearward side, ignition elements in said casing controlled by said guiding edge for the ignition of said propellant charge through said outflow nozzle, a pretensioned support spring engaging on one hand said bottom part and .on the other hand said ignition casing whereby said ignition casing under the pressure of said support spring 11 is urged towards the front on said
  • Ignition device for the launching of rockets comprising in combination a launcher tube, a launching trigget for triggering the ignition comprising a manually rotatable sleeve surrounding said tube having at its interior wall a groove and an opening extending from said groove through the wall of said sleeve, a bore extending through said tube wall, an interlocking ball extending into the interior of said tube guided in said bore and said groove, said ball being clear of the interior of said tube in correlation with said bore and said opening, a bottom part fastened to said tube at one end, a rocket axially displaceable in said tube having a propellant charge and an outflow nozzle communicating with said charge and directed towards the rear, a support shoulder engaging said interlocking ball, an ignition casing arranged in said bottom part behind said rocket axially displaceable in relation to said bottom part having a guiding edge on its rearward front side, said casing containing said ignition elements controlled by said guiding edge for the ignition of said propellant charge through said outflow nozzle,
  • said ignition elements comprise an ignition primer arranged opposite said outflow nozzle in said ignition casing for the ignition of said propellant charge, a firing pin axially displaceable in said ignition casing having an annular recess and being arranged in a safety position at a distance from said ignition primer, a firing pin spring supported under pretensioning on one hand on said ignition casing and on the other hand on said firing pin, a guide sleeve for said firing pin axially displaceable in said ignition casing having bores extending radially towards the exterior and which interlocks said guide sleeve with said bottom part, locking balls engaging said annular recess of said firing pin, said locking balls actuating said launching trigger by discontinuing the support of said support shoulder on said rocket when released by said guiding edge of said ignition casing at the axial displacement of the same towards the front and at the same time at the interlocked guide sleeve on said bottom part.
  • said ignition elements comprise an ignition primer arranged in said ignition casing opposite said outflow nozzle for the ignition of said propellant charge, a firing pin axially displaceable in said ignition casing having an annular recess and when in safety position arranged at adistance from said ignition primer, a pretensioned firing pin spring supported on one hand on said ignition casing and on the other hand on said firing pin, a guide sleeve for said firing pin axially displaceable in said ignition casing having bores extending radially towards the exterior, means interlocking said guide sleeve with said bottom part comprising interlocking balls engaged in said bores of said guide sleeve, and said annular recess of said firing pin, a tensioned firing pin spring cooperating with said interlocking means, said interlocking balls when actuating said launching trigger by discontinuing the support of said support shoulder on said rocket being released by said guiding edge of said ignition casing at an axial displacement of the same
  • Ignition device as claimed in claim 4 wherein a booster and ejector charge is arranged between said primer and said outflow nozzle which supports said primer during the start in combination with a disc displaceable in said tube and a bore connecting said nozzle.
  • Ignition device as claimed in claim 5 wherein a pretensioned pressure spring is arranged between said bottom part and said rocket for reinforcing the pressure of said support spring directed towards the front on said rocket.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Portable Nailing Machines And Staplers (AREA)
US601689A 1965-12-23 1966-12-14 Rocket launcher device Expired - Lifetime US3398640A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1774265A CH449472A (de) 1965-12-23 1965-12-23 Raketenabschusseinrichtung

Publications (1)

Publication Number Publication Date
US3398640A true US3398640A (en) 1968-08-27

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Application Number Title Priority Date Filing Date
US601689A Expired - Lifetime US3398640A (en) 1965-12-23 1966-12-14 Rocket launcher device

Country Status (9)

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US (1) US3398640A (enrdf_load_stackoverflow)
AT (1) AT267969B (enrdf_load_stackoverflow)
BE (1) BE691283A (enrdf_load_stackoverflow)
CH (1) CH449472A (enrdf_load_stackoverflow)
DE (1) DE1578033A1 (enrdf_load_stackoverflow)
FR (1) FR1506020A (enrdf_load_stackoverflow)
GB (1) GB1174049A (enrdf_load_stackoverflow)
NL (2) NL6616326A (enrdf_load_stackoverflow)
SE (1) SE320609B (enrdf_load_stackoverflow)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4895061A (en) * 1988-01-12 1990-01-23 Etienne Lacroix Tous Artifices S.A. Shoulder-borne weapon for use as rocket launcher
US5589655A (en) * 1994-04-15 1996-12-31 Giat Industries Electrical initiation device with contactor
WO2010036424A1 (en) * 2008-06-11 2010-04-01 Lockheed Martin Corporation Integrated pusher plate for a canister-or gun-launched projectile and system incorporating same
US9841256B2 (en) * 2016-01-17 2017-12-12 Wilcox Industries Corp. Combined launch and storage tube for missile
CN113606059A (zh) * 2021-06-22 2021-11-05 南阳北方向东工业有限公司 一种固体火箭安全保险结构及使用方法
CN113879569A (zh) * 2021-10-09 2022-01-04 航天科工火箭技术有限公司 低冲击解锁星箭分离装置及星箭分离系统
CN115096132A (zh) * 2022-06-22 2022-09-23 北京中科宇航技术有限公司 一种火箭支撑环调平装置及发射台

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2132034C1 (ru) * 1997-08-26 1999-06-20 Конструкторское бюро приборостроения Управляемая ракета
RU2584358C1 (ru) * 2015-02-17 2016-05-20 Акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Управляемая ракета
CN113800012B (zh) * 2021-09-30 2023-09-19 北京中科宇航技术有限公司 一种牵制释放装置及其系统

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1803366A (en) * 1929-08-30 1931-05-05 Charles C Stetson Signal rocket
US2436837A (en) * 1943-10-14 1948-03-02 John B Traylor Fuse for antitank mines
US2717042A (en) * 1950-03-31 1955-09-06 Specialties Dev Corp Impact operated valve
US2845002A (en) * 1957-07-29 1958-07-29 Jr Joseph I Ackerman Ejection device
US3242810A (en) * 1962-09-27 1966-03-29 Pointe Andre E La Water launched missile

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1803366A (en) * 1929-08-30 1931-05-05 Charles C Stetson Signal rocket
US2436837A (en) * 1943-10-14 1948-03-02 John B Traylor Fuse for antitank mines
US2717042A (en) * 1950-03-31 1955-09-06 Specialties Dev Corp Impact operated valve
US2845002A (en) * 1957-07-29 1958-07-29 Jr Joseph I Ackerman Ejection device
US3242810A (en) * 1962-09-27 1966-03-29 Pointe Andre E La Water launched missile

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4895061A (en) * 1988-01-12 1990-01-23 Etienne Lacroix Tous Artifices S.A. Shoulder-borne weapon for use as rocket launcher
US5589655A (en) * 1994-04-15 1996-12-31 Giat Industries Electrical initiation device with contactor
WO2010036424A1 (en) * 2008-06-11 2010-04-01 Lockheed Martin Corporation Integrated pusher plate for a canister-or gun-launched projectile and system incorporating same
US9841256B2 (en) * 2016-01-17 2017-12-12 Wilcox Industries Corp. Combined launch and storage tube for missile
CN113606059A (zh) * 2021-06-22 2021-11-05 南阳北方向东工业有限公司 一种固体火箭安全保险结构及使用方法
CN113879569A (zh) * 2021-10-09 2022-01-04 航天科工火箭技术有限公司 低冲击解锁星箭分离装置及星箭分离系统
CN115096132A (zh) * 2022-06-22 2022-09-23 北京中科宇航技术有限公司 一种火箭支撑环调平装置及发射台
CN115096132B (zh) * 2022-06-22 2023-09-29 北京中科宇航技术有限公司 一种火箭支撑环调平装置及发射台

Also Published As

Publication number Publication date
NL136198C (enrdf_load_stackoverflow)
NL6616326A (enrdf_load_stackoverflow) 1967-06-26
AT267969B (de) 1969-01-27
DE1578033A1 (de) 1970-12-03
CH449472A (de) 1967-12-31
BE691283A (enrdf_load_stackoverflow) 1967-05-16
SE320609B (enrdf_load_stackoverflow) 1970-02-09
GB1174049A (en) 1969-12-10
FR1506020A (fr) 1967-12-15

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